7x5 (7x5.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.6500 1.7975 0.0000 0.0000 0.3250 0.0000 0.2678 0.0000 0.1741 0.0000 0.0600 0.0000 0.0000 0.0800 0.6237 2.1195 0.0093 -0.2928 0.3208 0.0080 0.2612 1.0596 0.1629 0.1330 0.0672 0.0062 -0.0543 0.1600 0.5951 2.4245 0.0723 -0.5687 0.3162 0.0297 0.2547 4.1135 0.1516 0.1334 0.0864 0.0168 -0.0432 0.2400 0.5686 2.7124 0.2371 -0.7626 0.3115 0.0610 0.2484 8.9367 0.1413 0.1312 0.1135 0.0288 -0.0268 0.3200 0.5490 2.9833 0.5439 -0.7981 0.3068 0.0984 0.2424 15.1368 0.1331 0.1253 0.1456 0.0414 -0.0069 0.4000 0.5395 3.2371 1.0186 -0.6177 0.3024 0.1383 0.2365 22.0616 0.1276 0.1171 0.1804 0.0536 0.0150 0.4800 0.5410 3.4738 1.6621 -0.1906 0.2984 0.1773 0.2308 28.8597 0.1249 0.1080 0.2150 0.0645 0.0373 0.5600 0.5510 3.6935 2.4358 0.4676 0.2950 0.2120 0.2253 34.6941 0.1242 0.0989 0.2462 0.0732 0.0581 0.6400 0.5652 3.8961 3.2483 1.2740 0.2924 0.2387 0.2200 38.9311 0.1244 0.0906 0.2706 0.0791 0.0756 0.7200 0.5782 4.0817 3.9538 2.0681 0.2907 0.2540 0.2149 41.1531 0.1243 0.0838 0.2845 0.0812 0.0875 0.8000 0.5859 4.2502 4.3737 2.6285 0.2903 0.2545 0.2100 41.0270 0.1231 0.0788 0.2845 0.0787 0.0915 0.8802 0.5894 4.4020 4.5407 2.9425 0.2907 0.2446 0.2053 39.3862 0.1210 0.0750 0.2746 0.0732 0.0895 0.9643 0.5930 4.5427 4.6944 3.2550 0.2916 0.2342 0.2006 37.7679 0.1189 0.0712 0.2642 0.0682 0.0867 1.0486 0.5964 4.6649 4.8290 3.5497 0.2927 0.2237 0.1961 36.2387 0.1169 0.0676 0.2538 0.0639 0.0834 1.1329 0.5997 4.7681 4.9443 3.8218 0.2941 0.2131 0.1918 34.7828 0.1150 0.0643 0.2434 0.0602 0.0798 1.2172 0.6026 4.8524 5.0401 4.0680 0.2955 0.2026 0.1877 33.3849 0.1131 0.0612 0.2330 0.0569 0.0758 1.3016 0.6051 4.9177 5.1167 4.2851 0.2969 0.1920 0.1838 32.0332 0.1112 0.0584 0.2225 0.0539 0.0715 1.3859 0.6071 4.9641 5.1740 4.4707 0.2981 0.1813 0.1801 30.7184 0.1094 0.0557 0.2121 0.0513 0.0670 1.4702 0.6084 4.9915 5.2121 4.6225 0.2991 0.1707 0.1767 29.4333 0.1075 0.0533 0.2016 0.0490 0.0624 1.5545 0.6090 5.0000 5.2310 4.7389 0.2998 0.1599 0.1735 28.1724 0.1056 0.0511 0.1911 0.0469 0.0576 1.6388 0.6087 5.0000 5.2414 4.8285 0.3000 0.1492 0.1705 26.9773 0.1038 0.0491 0.1806 0.0450 0.0525 1.7231 0.6075 5.0000 5.2517 4.8993 0.2996 0.1386 0.1677 25.8769 0.1019 0.0473 0.1701 0.0433 0.0471 1.8074 0.6051 5.0000 5.2621 4.9513 0.2986 0.1279 0.1651 24.8613 0.0999 0.0457 0.1596 0.0417 0.0413 1.8917 0.6016 5.0000 5.2726 4.9847 0.2968 0.1173 0.1627 23.9218 0.0979 0.0441 0.1491 0.0401 0.0353 1.9760 0.5968 5.0000 5.2832 4.9993 0.2941 0.1068 0.1606 23.0509 0.0959 0.0427 0.1385 0.0385 0.0291 2.0603 0.5906 5.0000 5.2938 5.0000 0.2905 0.0963 0.1586 22.2412 0.0937 0.0412 0.1279 0.0367 0.0226 2.1447 0.5829 5.0000 5.3040 5.0001 0.2857 0.0859 0.1567 21.4850 0.0913 0.0396 0.1173 0.0345 0.0162 2.2290 0.5736 5.0000 5.3135 5.0002 0.2798 0.0757 0.1547 20.7769 0.0887 0.0379 0.1067 0.0320 0.0098 2.3133 0.5625 5.0000 5.3225 5.0002 0.2725 0.0656 0.1527 20.1122 0.0859 0.0359 0.0961 0.0289 0.0035 2.3976 0.5496 5.0000 5.3307 5.0002 0.2639 0.0556 0.1508 19.4866 0.0829 0.0338 0.0855 0.0254 -0.0028 2.4819 0.5347 5.0000 5.3380 5.0002 0.2537 0.0457 0.1488 18.8966 0.0796 0.0316 0.0748 0.0212 -0.0090 2.5662 0.5178 5.0000 5.3445 5.0002 0.2420 0.0360 0.1468 18.3385 0.0760 0.0293 0.0642 0.0163 -0.0152 2.6505 0.4987 5.0000 5.3499 5.0002 0.2284 0.0264 0.1449 17.8094 0.0722 0.0268 0.0535 0.0107 -0.0212 2.7348 0.4773 5.0000 5.3541 5.0001 0.2131 0.0169 0.1429 17.3062 0.0682 0.0242 0.0428 0.0043 -0.0272 2.8191 0.4535 5.0000 5.3567 5.0001 0.1958 0.0076 0.1409 16.8261 0.0639 0.0216 0.0321 -0.0029 -0.0330 2.9034 0.4272 5.0000 5.3575 5.0001 0.1765 -0.0016 0.1390 16.3663 0.0594 0.0189 0.0213 -0.0111 -0.0387 2.9878 0.3983 5.0000 5.3560 5.0001 0.1551 -0.0107 0.1370 15.9239 0.0546 0.0162 0.0106 -0.0203 -0.0443 3.0721 0.3667 4.9844 5.3358 4.9845 0.1313 -0.0197 0.1350 15.4525 0.0495 0.0136 -0.0002 -0.0306 -0.0496 3.1564 0.3322 4.9266 5.2692 4.9267 0.1053 -0.0286 0.1331 14.8792 0.0442 0.0110 -0.0110 -0.0420 -0.0547 3.2407 0.2948 4.8262 5.1539 4.8263 0.0767 -0.0375 0.1311 14.2041 0.0386 0.0086 -0.0218 -0.0546 -0.0594 3.3215 0.2560 4.6899 4.9946 4.6899 0.0469 -0.0459 0.1292 13.4591 0.0331 0.0064 -0.0321 -0.0679 -0.0639 3.3427 0.2454 4.6477 4.9445 4.6478 0.0387 -0.0481 0.1287 13.2474 0.0316 0.0059 -0.0349 -0.0715 -0.0650 3.3604 0.2364 4.6104 4.8997 4.6105 0.0318 -0.0499 0.1283 13.0649 0.0303 0.0054 -0.0371 -0.0746 -0.0660 3.3780 0.2271 4.5713 4.8521 4.5713 0.0246 -0.0517 0.1279 12.8770 0.0290 0.0050 -0.0394 -0.0778 -0.0669 3.3957 0.2162 4.5302 4.8020 4.5305 0.0158 -0.0539 0.1275 12.6840 0.0276 0.0045 -0.0421 -0.0819 -0.0681 3.4134 0.2024 4.4873 4.7491 4.4881 0.0042 -0.0566 0.1271 12.4858 0.0257 0.0040 -0.0456 -0.0875 -0.0697 3.4311 0.1848 4.4426 4.6932 4.4579 -0.0110 -0.0601 0.1267 12.2817 0.0234 0.0033 -0.0499 -0.0950 -0.0719 3.4487 0.1620 4.3959 4.6340 4.4428 -0.0314 -0.0645 0.1262 12.0710 0.0205 0.0026 -0.0556 -0.1054 -0.0747 3.4664 0.1296 4.3474 4.5712 4.4718 -0.0612 -0.0708 0.1258 11.8531 0.0163 0.0016 -0.0637 -0.1209 -0.0789 3.4841 0.0704 4.2970 4.5053 4.7966 -0.1173 -0.0823 0.1254 11.6292 0.0088 0.0005 -0.0784 -0.1506 -0.0868 3.5000 0.0080 4.2500 4.2500 4.2500 -0.1767 -0.0941 0.1250 10.9382 0.0010 0.0000 -0.0941 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.023676 TOTAL WEIGHT (Kg) = 0.010737 TOTAL VOLUME (IN**3) = 0.385705 TOTAL PROJECTED AREA (IN**2) = 3.3018 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000118 MOMENT OF INERTIA (Kg-M**2) = 0.000013 STATIC MOMENT, ONE SIDE (IN-LB) = 0.012974 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 91.122 INNER LIMIT (NORMALIZED BY RADIUS) = 0.093 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 33282.66 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.